EP1908923A1 - Vorrichtung zur Befestigung einer Leitschaufel in einem ringförmigen Gehäuse einer Strömungsmaschine, Turbinentriebwerk, mit einer solche Vorrichtung, und Verfahren zur Montage der Leitschaufel - Google Patents

Vorrichtung zur Befestigung einer Leitschaufel in einem ringförmigen Gehäuse einer Strömungsmaschine, Turbinentriebwerk, mit einer solche Vorrichtung, und Verfahren zur Montage der Leitschaufel Download PDF

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Publication number
EP1908923A1
EP1908923A1 EP07116774A EP07116774A EP1908923A1 EP 1908923 A1 EP1908923 A1 EP 1908923A1 EP 07116774 A EP07116774 A EP 07116774A EP 07116774 A EP07116774 A EP 07116774A EP 1908923 A1 EP1908923 A1 EP 1908923A1
Authority
EP
European Patent Office
Prior art keywords
blade
groove
platform
upstream
downstream
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP07116774A
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English (en)
French (fr)
Other versions
EP1908923B1 (de
Inventor
Olivier Belmonte
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1908923A1 publication Critical patent/EP1908923A1/de
Application granted granted Critical
Publication of EP1908923B1 publication Critical patent/EP1908923B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49947—Assembling or joining by applying separate fastener

Definitions

  • the present invention relates to the field of turbomachines, in particular turbofan engines.
  • a turbofan engine for the propulsion of transport airplanes comprises a generally upstream fan delivering an annular air flow with a primary central annular portion, which feeds the motor driving the fan and a secondary outer annular portion, which is ejected into the atmosphere while providing a significant fraction of the thrust.
  • the fan is contained in a fan casing externally defining the secondary flow.
  • a primary flow casing separates the primary stream from the secondary stream at a separation spout.
  • the present invention relates to the fixing and mounting of fixed vanes or stator vanes located downstream of the fan.
  • the mounting of the stator vanes in a turbojet engine is a mastered technique for medium-sized engines, such as CFM type engines.
  • This mounting technique is traditionally referred to as a "flush-mounted" type installation. It is used to mount the stator vanes, for example, in the secondary flow, between the fan casing and the primary flow casing to straighten the secondary flow in the axis of the motor as shown in Figure 1.
  • the fixed blade comprises a head formed of a platform with two edges, one forming an upstream edge and the other forming a downstream edge, a blade and a foot.
  • the fan casing comprises a circumferential groove, formed in its inner wall, with an upstream flank and a downstream flank, the head of the blade being retained by engagement of the platform in the groove.
  • the platform is held in the groove by means of two fixing screws which are screwed into the platform, respectively on each side of the flanks of the blade, as shown in FIG. 1.
  • the foot of the blade is retained by engagement in an opening in the primary flow casing.
  • the radial dimension of the engine is sufficient for a technician to manipulate the blades between the primary flow case and the fan case, that is to say, to pivot and translate them without risk of clashes with the casing or with a previously installed blade.
  • the vanes are accessible “from the rear”, that is to say downstream of the vanes in the secondary flow, which facilitates the maintenance and replacement of used blades.
  • the linear density of the blades at the periphery of the fan casing is higher for a small motor, the angular density remaining the same. This has several consequences at the level of fixing the vanes.
  • the platforms whose peripheral dimension is important to accommodate the fixing screws, are close to each other at the periphery of the housing. The insertion of the blades into the engine is then difficult, in particular when the blade is engaged in the groove of the fan casing, the transverse displacements being limited.
  • the fixing screws of the platform respectively disposed on each side of the flanks of the blade, are engaged between two adjacent blades, making their access difficult by means of the screwing devices.
  • the object of the invention is to overcome these drawbacks and to propose a fastening device and a method of mounting the vanes in an annular housing allowing rapid insertion and simple maintenance of the blades in the housing.
  • the Applicant proposes a device for fixing a fixed turbomachine blade in an annular casing of the turbomachine, the blade comprising a head formed of a platform with two edges, one forming an upstream edge and the another forming a downstream edge, a blade and a foot, the annular housing comprising a circumferential groove formed in its inner wall with an upstream flank and a downstream flank, the blade being retained by engagement of the platform in the groove, the edge upstream against the upstream side and the downstream edge against the downstream side of the groove, the downstream side of the groove being in the form of an axial opening groove upstream, the downstream edge of the platform being engaged in said downstream side and fastening means being attached to maintain the platform in the throat upstream, characterized in that the blade comprises a platform portion between the blade and the upstream edge pierced with a through opening arranged to receive said fixing means.
  • the downstream side of the groove does not require an attachment means, thus facilitating the insertion and maintenance of the blade in the housing.
  • Fixing means is only reported upstream of the blade which allows to fix the blades from the front of the engine and not on each side of the blades.
  • the fastening means are then easily accessible by fixing tools to make it faster to fix the platform in the groove.
  • the fixing means consists of a screw or two screws.
  • one or two screws are engaged near the upstream edge of the platform to maintain the latter in the groove.
  • the accessibility of the screws upstream allows easy handling of screwing devices.
  • a layer of elastomeric material is disposed between the downstream edge of the platform and the bottom of said groove.
  • the elastomeric material makes it possible to dampen the deflection of the blade from upstream to downstream when the flow of air from the blower is straightened by the blade.
  • the invention also relates to a turbofan engine with an upstream fan with a set of stationary vanes forming a flow rectifier downstream of the fan rotor, the vanes of which are retained inside the fan casing by the device of the invention. .
  • the blades are disposed between the fan casing and the primary flow casing, the blade root being engaged playfully in openings in said primary flow casing and a seal filling said clearance.
  • the game is filled with a seal to prevent the flow of air to rush into the primary flow casing.
  • the vanes and the primary flow casing are of metallic or composite material.
  • the invention also relates to the assembly method of the blades of the assembly, wherein the blade is engaged by the foot in said opening, the blade is tilted so as to engage the downstream edge of the platform in the groove downstream of the circumferential groove, it rotates the blade around the groove by bringing the blade upstream until the upstream edge of the platform comes into the groove, and the platform is secured to the housing with the means of fixation.
  • this mounting method makes it possible to mount vanes between the fan casing and the primary flow casing by limiting the transverse movements of the vanes with respect to the axis of the motor and by promoting radial displacements.
  • the seal is placed beforehand around the blade near the foot.
  • a layer of elastomeric material is placed between the downstream edge of the platform and the bottom of the groove.
  • the layer of elastomeric material is placed before the insertion of the blade to dampen its movement.
  • a stationary vane 10, or stator vane 10 is here installed in the channel of the secondary vein of a turbofan engine, downstream of a fan, between a fan casing 20 and a primary flow casing 30.
  • the blade 10 comprises a head 12 formed of a platform 14 with two edges, an upstream edge 141 and a downstream edge 142, a blade 11 and a foot 13.
  • the blades 10 and the casing primary flux 30 are here made of metal material, they could also be made of composite material.
  • the blade 10 is arranged radially in the vein, the foot 13 directed towards the axis of the engine, the blade 11 comprising a leading edge 151 and a trailing edge 152, the platform 14 being substantially perpendicular to the blade 11.
  • the platform 14 is here formed of a parallelepipedal block whose thickness decreases between the upstream edge 141 and the downstream edge 142, the upstream edge 141 being terminated at its upstream end by a recess 1411 formed on the face of the platform in contact. with the casing 20, this recess 1411 facilitating the insertion of the platform 14 into said casing 20.
  • the downstream edge has a rounded portion 1421.
  • the platform 14 is pierced by two through openings 17, 18 disposed at the level of a platform portion between the upstream edge 141 and the blade 11.
  • the openings 17, 18 are each arranged to receive a fixing means 40.
  • the fan casing 20 comprises a circumferential groove 23 formed in its inner wall in which the platform 14 is inserted.
  • the groove 23 comprises an upstream flank 21 and a downstream flank 22.
  • the downstream flank 22 has a shape of circular section groove, axial opening upstream.
  • the blade 10 is retained by engagement of its platform 14 in the groove 23, the upstream edge 141 against the upstream flank 21 and the downstream edge 142 against the downstream flank 22 of the groove 23.
  • the rounded portion 1421 of the downstream edge 142 cooperates with the groove 22.
  • a game is formed between the upstream flank 141 and the upstream edge 21 to facilitate the insertion of the platform 14 into the groove 23.
  • a layer of damping elastomeric material 60 is disposed between the downstream edge 142 of the platform 14 and the bottom of said groove 22.
  • the elastomer 60 limits the deflection of the blade 10 when it is subjected to the fluctuations of the airflow from the blower.
  • the layer of elastomeric material 60 comprises a locking tongue 61 projecting radially cooperating with a recess 25 arranged in the inner wall of the groove 23 near the groove 22, the tongue 61 maintaining the elastomeric layer 60 in the bottom of the groove 22.
  • the platform 14 is retained in the groove 23 by means of screws 40 passing through the openings 17, 18, as shown in FIG. 3. With reference to FIG. 4, two screws 40 are here engaged at the upstream edge 141 to maintain the head 12 of dawn 10.
  • the foot 13 is engaged with a clearance in a through opening 31 formed in the primary flow casing 30, as shown in FIG. 5.
  • a ring-shaped seal 50 is threaded on the blade 11 at the foot 13 thus making the engagement of the blade 10 in the housing 30 impermeable to air.
  • the mounting of the vanes 10 can thus be performed from the front.
  • the elastomer seal 60 is firstly inserted in the downstream groove 22 and is blocked by means of the radial projection tongue 61 in the recess 25 of the groove 23. The elastomer 60 is then secured to the bottom groove 22.
  • annular seal 50 is threaded onto the blade 11 by the foot 13 of the blade 10 which is raised higher than its final position so as not to clutter the end of the foot 13 of the dawn 10.
  • the inclined blade 13 is then presented, the foot 13 directed downstream, with the seal 50 raised on the blade 11, in the through opening 31 of the primary flow casing 30.
  • the foot is pressed from upstream to the downstream farther than its final position in said housing 30, in order to maintain a clearance to straighten the blade 10.
  • the head 12 of the blade 10 is then raised downstream, the foot 13 being guided in the opening 31, the rounded portion 1421 of the downstream edge being inserted into the groove 22 of the groove 23, the groove 22 having been previously coated with the elastomer layer 60.
  • the blade 10 is then rotated around the groove 22 by bringing the blade 10 upstream until the upstream edge 141 of the platform 14 comes into contact with the bottom of the groove 23, the clearance between the upstream flank 21 and the upstream edge 141 facilitating the insertion of the platform 14 into the groove 23.
  • the annular seal 50 is then slid along the blade 11, the seal 50 filling the gap between the blade 10 and the opening 31.
  • the seal 50 here made of elastomeric material, can be compressed during its insertion, the seal 50 relaxing once disposed between the blade 10 and the opening 30, making the engagement of the blade 10 in the airtight housing 20.
  • the platform 14 is secured to the casing 20 by screwing the screws 40 at the upstream edge 141 of the platform 14 to hold it in the groove 23.
  • the screwing is performed with screwing tools, the upstream edge 141 being easily accessible. upstream of the engine.
  • the air coming from the fan is straightened in the axis of the turbojet, the seal 50 preventing air from rushing into the casing of the primary flow 30 and the elastomer layer 60 allowing cushion the deflection of dawn 10.
  • the described blade assembly and disassembly methods are well suited for motors with a high linear density of vanes at the circumference of the casing 20. These methods are therefore particularly suitable for small engines whose blades are very close to each other.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP07116774A 2006-09-26 2007-09-19 Vorrichtung zur Befestigung einer Leitschaufel in einem ringförmigen Gehäuse einer Strömungsmaschine, Turbinentriebwerk mit einer solchen Vorrichtung, und Verfahren zur Montage der Leitschaufel Active EP1908923B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0653952A FR2906296A1 (fr) 2006-09-26 2006-09-26 Dispositif de fixation d'une aube fixe dans un carter annulaire de turbomachine, turboreacteur incorporant le dispositif et procede de montage de l'aube.

Publications (2)

Publication Number Publication Date
EP1908923A1 true EP1908923A1 (de) 2008-04-09
EP1908923B1 EP1908923B1 (de) 2010-01-27

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EP07116774A Active EP1908923B1 (de) 2006-09-26 2007-09-19 Vorrichtung zur Befestigung einer Leitschaufel in einem ringförmigen Gehäuse einer Strömungsmaschine, Turbinentriebwerk mit einer solchen Vorrichtung, und Verfahren zur Montage der Leitschaufel

Country Status (7)

Country Link
US (1) US7959408B2 (de)
EP (1) EP1908923B1 (de)
CN (1) CN101153547B (de)
CA (1) CA2603119C (de)
DE (1) DE602007004547D1 (de)
FR (1) FR2906296A1 (de)
RU (1) RU2435037C2 (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2075412A1 (de) * 2007-12-26 2009-07-01 Techspace aero Vorrichtung zur Befestigung durch Verschraubung von Leitschaufeln an den Mantelring einer Statorstufe einer Strömungsmaschine und entsprechendes Befestigungsverfahren durch Verschraubung
EP2194230A1 (de) * 2008-12-05 2010-06-09 Siemens Aktiengesellschaft Leitschaufelanordnung für eine Axialturbomaschine
WO2011128551A2 (fr) 2010-04-14 2011-10-20 Snecma Dispositif redresseur pour turbomachine
FR2989414A1 (fr) * 2012-04-16 2013-10-18 Snecma Procede et un outillage de montage d'un etage redresseur
EP2735708A1 (de) * 2012-11-22 2014-05-28 Rolls-Royce Deutschland Ltd & Co KG Flugzeugtriebwerksdichtungsanordnung
FR3038351A1 (fr) * 2015-06-30 2017-01-06 Snecma Redresseur de soufflante pour turbomachine a double flux
FR3074219A1 (fr) * 2017-11-30 2019-05-31 Safran Aircraft Engines Ensemble de turbomachine avec une aube de stator a plateforme integree et moyens de maintien.

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FR2920032B1 (fr) * 2007-08-13 2014-08-22 Snecma Diffuseur d'une turbomachine
ATE556195T1 (de) * 2009-02-05 2012-05-15 Siemens Ag Ringförmige schaufelanordnung für einen gasturbinenmotor
US8966756B2 (en) * 2011-01-20 2015-03-03 United Technologies Corporation Gas turbine engine stator vane assembly
US8966755B2 (en) 2011-01-20 2015-03-03 United Technologies Corporation Assembly fixture for a stator vane assembly
US9303531B2 (en) * 2011-12-09 2016-04-05 General Electric Company Quick engine change assembly for outlet guide vanes
JP5962887B2 (ja) * 2012-02-02 2016-08-03 株式会社Ihi 翼の連結部構造及びこれを用いたジェットエンジン
FR2989130B1 (fr) * 2012-04-05 2014-03-28 Snecma Etage redresseur de compresseur pour une turbomachine
US9777584B2 (en) 2013-03-07 2017-10-03 Rolls-Royce Plc Outboard insertion system of variable guide vanes or stationary vanes
US10047763B2 (en) * 2015-12-14 2018-08-14 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
ES2881949T3 (es) 2016-10-27 2021-11-30 Gilead Sciences Inc Forma cristalina de base libre de darunavir
US10900364B2 (en) * 2017-07-12 2021-01-26 Raytheon Technologies Corporation Gas turbine engine stator vane support
CN107542500B (zh) * 2017-09-30 2019-05-24 中国航发沈阳发动机研究所 航空发动机风扇机匣及其装配方法
CN109882255B (zh) * 2019-03-01 2021-10-19 西安航天动力研究所 带叶片型线槽的涡轮静子顶部封严限位结构
CN109968241A (zh) * 2019-04-03 2019-07-05 哈尔滨汽轮机厂有限责任公司 一种汽轮机静叶片整圈预装配盘及预装配方法
US11828197B2 (en) 2021-12-03 2023-11-28 Rolls-Royce North American Technologies Inc. Outlet guide vane mounting assembly for turbine engines
CN114458628B (zh) * 2022-04-12 2022-06-24 广东威灵电机制造有限公司 风机及电器设备

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0953729A1 (de) * 1998-05-01 1999-11-03 Techspace aero Leitbeschaufelung für eine Turbomaschine
EP1167693A2 (de) * 2000-06-30 2002-01-02 General Electric Company Leitschaufelplattformen
EP1219785A1 (de) * 2000-12-19 2002-07-03 United Technologies Corporation Befestigungsanordnung für Turbinenleitschaufeln
FR2832179A1 (fr) * 2001-11-14 2003-05-16 Snecma Moteurs Stator d'une machine et procedes de montage et demontage
US20040062652A1 (en) * 2002-09-30 2004-04-01 Carl Grant Apparatus and method for damping vibrations between a compressor stator vane and a casing of a gas turbine engine

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US5584654A (en) * 1995-12-22 1996-12-17 General Electric Company Gas turbine engine fan stator
US6234750B1 (en) * 1999-03-12 2001-05-22 General Electric Company Interlocked compressor stator
DE50011923D1 (de) * 2000-12-27 2006-01-26 Siemens Ag Gasturbinenschaufel und Gasturbine
US7481618B2 (en) * 2005-12-21 2009-01-27 Rolls-Royce Plc Mounting arrangement

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0953729A1 (de) * 1998-05-01 1999-11-03 Techspace aero Leitbeschaufelung für eine Turbomaschine
EP1167693A2 (de) * 2000-06-30 2002-01-02 General Electric Company Leitschaufelplattformen
EP1219785A1 (de) * 2000-12-19 2002-07-03 United Technologies Corporation Befestigungsanordnung für Turbinenleitschaufeln
FR2832179A1 (fr) * 2001-11-14 2003-05-16 Snecma Moteurs Stator d'une machine et procedes de montage et demontage
US20040062652A1 (en) * 2002-09-30 2004-04-01 Carl Grant Apparatus and method for damping vibrations between a compressor stator vane and a casing of a gas turbine engine

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2075412A1 (de) * 2007-12-26 2009-07-01 Techspace aero Vorrichtung zur Befestigung durch Verschraubung von Leitschaufeln an den Mantelring einer Statorstufe einer Strömungsmaschine und entsprechendes Befestigungsverfahren durch Verschraubung
EP2194230A1 (de) * 2008-12-05 2010-06-09 Siemens Aktiengesellschaft Leitschaufelanordnung für eine Axialturbomaschine
WO2011128551A2 (fr) 2010-04-14 2011-10-20 Snecma Dispositif redresseur pour turbomachine
FR2958980A1 (fr) * 2010-04-14 2011-10-21 Snecma Dispositif redresseur pour turbomachine
WO2011128551A3 (fr) * 2010-04-14 2011-12-08 Snecma Dispositif redresseur pour turbomachine
US9157454B2 (en) 2010-04-14 2015-10-13 Snecma Flow straightener device for turbomachine
WO2013156715A1 (fr) * 2012-04-16 2013-10-24 Snecma Procédé et un outillage de montage d'un étage redresseur
FR2989414A1 (fr) * 2012-04-16 2013-10-18 Snecma Procede et un outillage de montage d'un etage redresseur
US9605563B2 (en) 2012-04-16 2017-03-28 Snecma Method and tooling for assembling a guide vane stage
EP2735708A1 (de) * 2012-11-22 2014-05-28 Rolls-Royce Deutschland Ltd & Co KG Flugzeugtriebwerksdichtungsanordnung
US9932846B2 (en) 2012-11-22 2018-04-03 Rolls-Royce Deutschland Ltd & Co Kg Aeroengine sealing arrangement
FR3038351A1 (fr) * 2015-06-30 2017-01-06 Snecma Redresseur de soufflante pour turbomachine a double flux
FR3074219A1 (fr) * 2017-11-30 2019-05-31 Safran Aircraft Engines Ensemble de turbomachine avec une aube de stator a plateforme integree et moyens de maintien.

Also Published As

Publication number Publication date
EP1908923B1 (de) 2010-01-27
RU2007135207A (ru) 2009-03-27
DE602007004547D1 (de) 2010-03-18
RU2435037C2 (ru) 2011-11-27
CN101153547A (zh) 2008-04-02
CA2603119C (fr) 2014-02-25
FR2906296A1 (fr) 2008-03-28
CN101153547B (zh) 2012-10-24
US7959408B2 (en) 2011-06-14
US20080075588A1 (en) 2008-03-27
CA2603119A1 (fr) 2008-03-26

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